Airfoil Tools
Search 1638 airfoils

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Your Reynold number range is 50,000 to 1,000,000. (set)

Airfoil database search

Search the 1638 airfoils available in the databases filtering by name, thickness and camber. Click on an airfoil image to display a larger preview picture. There are links to the original airfoil source and dat file and the details page with polar diagrams for a range of Reynolds numbers.

(s1223-il) S1223		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1223 high lift low Reynolds number airfoil Max thickness 12.1% at 19.8% chord Max camber 8.1% at 49% chord Max Cl/Cd 75.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca65410-il) NACA 65-410		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-410 airfoil Max thickness 10% at 39.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 75.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe281-il) GOE 281 (DAIMLER XII) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 281 (DAIMLER XII) airfoil Max thickness 8% at 30% chord Max camber 4.5% at 40% chord Max Cl/Cd 75.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe328-il) GOE 328 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 328 airfoil Max thickness 8.2% at 30% chord Max camber 4.3% at 30% chord Max Cl/Cd 75.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e587-il) EPPLER 587 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E587 sailplane airfoil Max thickness 16.6% at 41.1% chord Max camber 4.2% at 51.2% chord Max Cl/Cd 75.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(fx60126-il) WORTMANN FX 60-126 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 60-126 airfoil Max thickness 12.6% at 27.9% chord Max camber 3.6% at 56.5% chord Max Cl/Cd 75.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe329-il) GOE 329 (PFALZ 58) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 329 (Pfalz 58) airfoil Max thickness 10.2% at 29.9% chord Max camber 5.5% at 29.9% chord Max Cl/Cd 75.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(clarkv-il) CLARK V AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK V airfoil Max thickness 11.6% at 30% chord Max camber 3.4% at 50% chord Max Cl/Cd 75.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe319-il) GOE 319 (HANSA-BRANDENBURG II) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 319 (Hansa-Brandenburg II) airfoil Max thickness 10.3% at 29.8% chord Max camber 5.8% at 29.8% chord Max Cl/Cd 75.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe476-il) GOE 476 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 476 airfoil Max thickness 14.5% at 29.5% chord Max camber 5.2% at 39.5% chord Max Cl/Cd 75.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database